The feasability of operating tilting-prop-rotor aircraft at high speeds is examined by calculating the performance, stability, and maneuverability of representative configurations. The rotor performance is examined in high-speed cruise and in hover. The whirl-flutter stability of the coupled-wing and rotor motion is calculated in the cruise mode. Maneuverability is examined in terms of the rotor-thrust limit during turns in helicopter configuration. Rotor airfoils, rotor-hub configuration, wing airfoil, and airframe structural weights representing demonstrated advanced technology are discussed. Key rotor and airframe parameters are optimized for high-speed performance and stability. The basic aircraft-design parameters are optimized for minimum gross weight. To provide a focus for the calculations, two high-speed tilt-rotor aircraft are considered: a 46-passenger, civil transport and an air-combat/escort fighter, both with design speeds of about 400 knots. It is concluded that such high-speed tilt-rotor aircraft are quite practical.


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    Titel :

    Calculated performance, stability, and maneuverability of high-speed tilting-prop-rotor aircraft


    Beteiligte:
    Johnson, Wayne (Autor:in) / Lau, Benton H. (Autor:in) / Bowles, Jeffrey V. (Autor:in)

    Erscheinungsdatum :

    1986-09-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Calculated performance, stability and maneuverability of high-speed tilting-prop-rotor aircraft

    Johnson, Wayne / Lau, Benton H. / Bowles, Jeffrey V. | NTRS | 1986



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